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The KERAMIK Thermal Protection System Experiment on the FOTON-M2 Mission

Reimer, Thomas (2006) The KERAMIK Thermal Protection System Experiment on the FOTON-M2 Mission. In: 5th European Workshop on Thermal Protection Systems and Hot Structures. Thermal Protection Systems and Hot Structures (5th Workshop), 2006-05-17 - 2006-05-19, Noordwijk, NL. ISBN 92-9092-942-1. ISSN 1609-042X.



On June 16, 2005 the re-entry module of the Russian FOTON-M2 spacecraft made a successful landing after a 16-day microgravity mission in space. On board was also the “KERAMIK” experiment by the Institute of Structures and Design of the German Aerospace Center (DLR) in Stuttgart, Germany. The re-entry technology experiment was aiming for the first flight of a Thermal Protection System (TPS) with it´s structural components designed and manufactured fully in C/C-SiC, a Ceramic Matrix Composite (CMC) material developed by DLR. The experiment had a surface diameter of 340 mm and was located on the exterior of the re-entry spacecraft embedded into the ablative heat shield. The emphasis of the experiment was on the system aspects of the TPS design. It included two stiffened surface panels each fixed to three structural posts with a special fastener type, all components made from the C/C-SiC material. The experiment deliberately included a gap between the panels and a surrounding close-out ring to test the performance of a dedicated seal in that area. In addition to the structural aspects of the experiment, a set of different oxidation protection coatings was applied to the surface of one of the panels to conduct a comparative test under flight conditions. The position of the experiment was carefully selected with regard to the aerothermodynamic environment. Since the experiment technology aims at re-usable vehicles, a position in the stagnation area of the ballistic re-entry module would have resulted in excessive heat loads. Therefore a location was preferred at an angle of almost 90° relative to the flight direction. The temperature data that was measured during re-entry shows that the surface temperature was close to 1500°C, which was in the targeted range. The structural components on the surface of the experiment were in an excellent condition as a visual inspection immediately after landing revealed.

Item URL in elib:https://elib.dlr.de/46736/
Document Type:Conference or Workshop Item (Speech, Paper)
Title:The KERAMIK Thermal Protection System Experiment on the FOTON-M2 Mission
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Date:17 May 2006
Journal or Publication Title:5th European Workshop on Thermal Protection Systems and Hot Structures
Refereed publication:No
Open Access:Yes
Gold Open Access:No
In ISI Web of Science:No
EditorsEmailEditor's ORCID iD
Keywords:Thermal Protection System, Ceramic Matrix Composite, C-SiC, C/C-SiC, Foton, re-entry, reentry, entry, heat shield, ablation, oxidation protection
Event Title:Thermal Protection Systems and Hot Structures (5th Workshop)
Event Location:Noordwijk, NL
Event Type:international Conference
Event Dates:2006-05-17 - 2006-05-19
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Space (old)
HGF - Program Themes:W RP - Raumtransport
DLR - Research area:Space
DLR - Program:W RP - Raumtransport
DLR - Research theme (Project):W - Grundlagen Raumtransport - Innovativer Thermalschutz (old)
Location: Stuttgart
Institutes and Institutions:Institute of Structures and Design > Space Structural Components
Deposited By: Reimer, Thomas
Deposited On:10 Jan 2007
Last Modified:31 Jul 2019 19:18

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